CN104321253A - Ventilation system and method of assembly - Google Patents
Ventilation system and method of assembly Download PDFInfo
- Publication number
- CN104321253A CN104321253A CN201280054124.7A CN201280054124A CN104321253A CN 104321253 A CN104321253 A CN 104321253A CN 201280054124 A CN201280054124 A CN 201280054124A CN 104321253 A CN104321253 A CN 104321253A
- Authority
- CN
- China
- Prior art keywords
- nozzle
- valve
- ventilation system
- air stream
- silencer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60H—ARRANGEMENTS OF HEATING, COOLING, VENTILATING OR OTHER AIR-TREATING DEVICES SPECIALLY ADAPTED FOR PASSENGER OR GOODS SPACES OF VEHICLES
- B60H1/00—Heating, cooling or ventilating [HVAC] devices
- B60H1/34—Nozzles; Air-diffusers
- B60H1/3414—Nozzles; Air-diffusers with means for adjusting the air stream direction
- B60H1/3435—Nozzles; Air-diffusers with means for adjusting the air stream direction using only a pivoting frame
- B60H1/3442—Nozzles; Air-diffusers with means for adjusting the air stream direction using only a pivoting frame the frame being spherical
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60H—ARRANGEMENTS OF HEATING, COOLING, VENTILATING OR OTHER AIR-TREATING DEVICES SPECIALLY ADAPTED FOR PASSENGER OR GOODS SPACES OF VEHICLES
- B60H1/00—Heating, cooling or ventilating [HVAC] devices
- B60H1/34—Nozzles; Air-diffusers
- B60H2001/3471—Details of actuators
- B60H2001/3478—Details of actuators acting on additional damper doors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D2013/003—Cabin ventilation nozzles
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
Abstract
A ventilation system for ventilating a passenger compartment of an aircraft is disclosed herein. The ventilation system includes, but is not limited to, a nozzle that is adapted to be mounted proximate an interior of the aircraft and that is configured to direct a stream of air into the passenger compartment. The ventilation system further includes a valve that is spaced apart from the nozzle and positioned upstream of the nozzle, the valve configured to control a flow of air to the nozzle. The ventilation system still further includes a conduit that fluidly couples the valve to the nozzle. The conduit is configured to convey the flow of air from the valve to the nozzle.
Description
The cross reference of related application
This application claims the preceence that the sequence number submitted on November 3rd, 2011 is U.S.'s non-provisional application of 13/288,796.
Technical field
The present invention relates generally to the assemble method of ventilation system and ventilation system.
Background technology
Modern passenger aircraft generally includes ventilation system, and it is configured to the air stream after by cooling (or heating) and guides towards every passenger on aircraft.Typically, provide adjustable nozzle can to every passenger, it is installed in overhead bin, and passenger can operate it and be reorientated to control the direction of air stream.Such as, nozzle can be configured to spherical, and can be arranged in the spherical bearing in overhead bin.By making ball nozzle move in spherical bearing, passenger can control the direction of air stream.
Nozzle also comprises passenger can the pile-up valve of random open and/or closed.Typically, this valve is needle valve, and described needle valve comprises fibula (pintle) and opening, and described opening is configured to engage with fibula and blocked by fibula.When actuator on passenger outwards winding nozzle and/or when screwing on nozzle actuator, fibula is retracted and/or is extended and causes needle valve by open and/or closed respectively.When needle valve is opened, air stream flows out from nozzle, and when needle valve cuts out, air stream is cut off.Therefore, above-mentioned traditional ventilation system allows every passenger arbitrarily to open and close air stream, and towards desired goal directed air stream.This level of control provides traveling comfort to passenger.This pattern of adjustable ventilation is commonly called " supply gas (gasper) " in aerospace applications.
Have been found that the another feature of the above-mentioned ventilation system meeting birdman is the air stream being produced high relative velocity by this ventilation system.The air stream having confirmed to produce high relative velocity for make the passenger be in aircraft cockpit feel nice and cool/warm for be very effective.The air stream of high speed is obtained usually used as the result of nozzle structure.In traditional nozzle, the upstream portion of nozzle has the diameter being greater than nozzle downstream part.Therefore, when the air stream of relative low speeds degree enters in nozzle, the area of passage that air circulation crosses it starts constriction.When air stream continues to flow downward by this constriction reinforcement during nozzle.When air drift dynamic by nozzle time, this constriction causes air stream to accelerate, to maintain constant mass flowrate.
Although above-mentioned ventilation system enough, still has room for improvement.Air flow through the flowing of nozzle and acceleration cause when air stream leaves nozzle significantly fizz.In numerous applications, by ventilation system cause fizz can not be louder than the background noise in aircraft cabin significantly, be therefore acceptable.But, some aircrafts (such as, the jet plane of private corporation) design, build and/or be configured at aircraft run duration providing the background noise that level reduces compared with conventional commercial aircraft in cabin.In this aircraft, the noise produced by ventilation system can be quite significantly and/or be unacceptable for potential customers.
Ventilation system was made quietly to attempt being included in nozzle and use dissimilar valve in the past.Other is attempted comprising and reduces the air pressure that air flows through this valve, and this produces again the air stream compared with low velocity.These solutions are not actvies.Such as, although use dissimilar valve to produce the reading of decibel reduction to a certain extent at nozzle exit in nozzle, it is inadequate that this volume reduces.In addition, although confirmed that to be left in noise decibel level that nozzle produces by air stream be actv. reducing for reduction that air flows through the air pressure of nozzle, this reduction of air pressure has significantly reduced the air flow velocity leaving nozzle.This reduction on the air flow velocity leaving nozzle causes unacceptable reduction in the ability validity of air stream cooling/warm birdman.
Therefore, ventilation system that is relatively quiet, high velocity air stream is produced desirable to provide a kind of.In addition, desirable to provide the assemble method of this ventilation system.In addition, other characteristic sum characteristic of wishing will become apparent with aforesaid technical field and background technology by reference to the accompanying drawings from detailed description subsequently and appended claim.
Summary of the invention
The assemble method of a kind of ventilation system for ventilating to the passenger cabin of aircraft and a kind of ventilation system for ventilating to the passenger cabin of aircraft is disclosed herein.
In the first nonrestrictive embodiment, ventilation system includes but not limited to nozzle, and it is suitable for being arranged near interior of aircraft, and it is configured to air stream to be directed to passenger compartments.This ventilation system also comprises valve, and itself and nozzle pitch are opened and it is positioned at the upstream side of described nozzle.This valve is configured to the air flowing controlling to nozzle.Ventilation system also comprises conduit valve being fluidly couple to nozzle further.Air flowing is sent to nozzle from valve by this conduits configurations one-tenth.
In another nonrestrictive embodiment, ventilation system includes but not limited to nozzle, and it is suitable for being arranged on the inner portions of aircraft and it is configured to air stream to be directed to passenger compartments.This ventilation system also comprises valve, and itself and nozzle pitch are opened and it is positioned at the upstream side of described nozzle.This valve is configured to the air flowing controlling to nozzle.Ventilation system also comprises conduit valve being fluidly couple to nozzle further.Air flowing is sent to nozzle from valve by this conduits configurations one-tenth.Ventilation system also comprises silencer further, and it fluidly connects with conduit, air flow stream is moved and passes through silencer.Silencer is configured to when air flow stream is moved by absorbing the acoustic energy flowed from air during silencer.
In another nonrestrictive embodiment, the method comprises the following steps: near passenger cabin nozzle being arranged on aircraft, and described like this nozzle placement becomes to ventilate to passenger compartments.The method is further comprising the steps of: be positioned at by valve in the position of opening with nozzle pitch near passenger cabin.The method is further comprising the steps of: by tubes connection between the output and the entrance of nozzle of described valve, makes valve and nozzle via conduit and fluidly couples each other and be configured to provide ventilation to the passenger cabin of aircraft.
Accompanying drawing explanation
Hereafter by conjunction with following accompanying drawing, present invention is described, wherein identical Reference numeral refers to identical element, and:
Fig. 1 is the environmental view that aircraft cabin cabin interior is shown, it comprises the embodiment of the ventilation system prepared according to disclosure training centre;
Fig. 2 is the transparent view that overhead bin housing inner portion is shown, it holds the embodiment of disclosure ventilation system;
Fig. 3 is the schematic diagram that ventilation system shown in Fig. 2 is shown;
Fig. 4 is the more detailed cutaway view of the nozzle that ventilation system shown in Fig. 3 is shown;
Fig. 5 is the axial view of getting above nozzle shown in Fig. 3;
Fig. 6 is the transparent view that fin (tab) member embodiment being suitable for using together with the nozzle shown in Fig. 3 is shown; And
Fig. 7 is the diagram of circuit of the assemble method embodiment that ventilation system shown in Fig. 3 is shown.
Detailed description of the invention
Detailed description is below only exemplary in itself, and not intention limits the present invention or application of the present invention and purposes.In addition, never intention is subject to the constraint of any theory that the background technology above or detailed description of the invention part below present.
A kind of ventilation system of improvement is disclosed herein.Compared with traditional ventilation system, valve removes from nozzle and valve is reorientated upstream side in the air stream by ventilation system of the present disclosure.As used in this article like that, term " upstream side " should refer to by the contrary direction of the airflow direction of ventilation system, and term " downstream " should refer to by the identical direction of the airflow direction of ventilation system.By by valve location upstream side in the air stream, the noise produced by the air stream by valve (such as, as the result of turbulent flow) is away from nozzle and have an opportunity to advance to nozzle along with air from valve and dissipate.By not wishing the mechanism of noise and do not wish to provide this additional distance between the opening that noise is dispersed into passenger compartments producing major part, the decibel level of not wishing noise or volume that can be heard by passenger in cabin significantly can be reduced.Extra improvement makes it possible to further reduce the volume of not wishing noise.Such as, in certain embodiments, ventilation system will comprise the silencer be positioned between described valve and nozzle.In other embodiments, fibula can be positioned in nozzle so that the more upstream side that air stream accelerates position originally at it accelerates.Air stream accelerates to enter into can produce undesirable noise in the high velocity air stream at nozzle place.By using fibula to make acceleration move to upstream side, the volume of not wishing noise arriving passenger will be weakened.
By check with this application diagram with check the more deep understanding that can to obtain together with detailed description subsequently above-mentioned ventilation system and ventilation system assemble method.
Fig. 1 is the environmental view of the inside, cabin, cabin 10 of the commercial jet plane that private corporation is shown.Although comprised herein discussion background is the commercial jet plane relative to private corporation, but should be understood that, instruction of the present disclosure is applicable to all types of aircraft, described aircraft includes but not limited to the aircraft that private screw propeller drives, private jet, commercial jet airliners, the passenger plane that commercial screw propeller drives, cargo aircraft, military aircraft etc.In addition, be suitable for using aboard although ventilation system disclosed herein is described as, should be understood that, ventilation system of the present invention is applicable to all types of vehicle.Such as but and nonrestrictive, ventilation system disclosed herein can be implemented on the transportation means of automobile, city motor bus, train, boats and ships, spacecraft and other type any.In addition, ventilation system disclosed herein is not limited to implement on a vehicle, but is also applicable to tent, house, building, stadium, theater and other permanent and/or semi-permanent structure.
Cabin, cabin 10 comprises the embodiment of the ventilation system 12 prepared according to disclosure training centre.In the illustrated embodiment in which, ventilation system 12 is housed inside in overhead bin 14, and described overhead bin 14 is configured to hold ventilation system 12 and support ventilation system 12 and support the miscellaneous equipment needed for airplane operation.Ventilation system 12 comprises nozzle 16.Nozzle 16 has the layout that ball is in type in spherical bearing, and this layout has nozzle mount pad (not shown at Fig. 1), its allow passenger operation nozzle 16 and correspondingly by the air stream of being discharged by ventilation system 12 towards desired regional guidance.
Passenger seat 18 is positioned at the below of ventilation system 12, and is configured to receive birdman.In the illustrated embodiment in which, single ventilation system 12 is specifically designed to cooling and/or heats the passenger be seated on single passenger seat 18.In other embodiments, multiple ventilation system 12 can be configured to air stream to guide towards single passenger seat 18.In other embodiments, single ventilation system 12 can be configured to multiple air stream to be provided to multiple passenger seat 18.
Continuing with reference to Fig. 1, Fig. 2 is the transparent view that overhead bin 14 interior section is shown.Ventilation system 12 is installed on the bottom panel 20 of overhead bin 14.Ventilation system 12 comprises nozzle 16 (see Fig. 1), nozzle mount pad 22, flexible tube section 24, silencer 26, flexible tube section 28 and electronically actuated valve 30.
Nozzle mount pad 22 and nozzle 16 are couple to each other with the layout that ball is in spherical bearing, and therefore, nozzle 16 can rotate around X-axis and Y-axis two axles relative to nozzle mount pad 22.Therefore, the passenger be seated at below nozzle 16 can touch the air stream of being discharged by nozzle 16, and arbitrarily by the air circulation of being discharged by nozzle 16 towards desired regional guidance.Nozzle mount pad 22 can comprise one or more opening, to receive the fastener that can be used for being fixed to by nozzle mount pad 22 on bottom panel 20.
Pipeline section 34 extends out from the rear portion of nozzle mount pad 22.Pipeline section 34 is bending to be directed in nozzle mount pad 22 by the air stream from flexible tube section 24.Nozzle mount pad 22, nozzle 16 and pipeline section 34 can be made up of any suitable material, and described material includes but not limited to plastics, metal, polymeric material and effectively can comprise other suitable material any of the air stream by each corresponding assembly.
Flexible tube section 24 and flexible tube section 28 can comprise the flexible pipe of any traditional type effectively comprising and draw airflow guiding.Flexible tube section 24 and flexible tube section 28 can be made up of any suitable material, and described material includes but not limited to rubber, plastics and polymeric material.In other embodiments, flexible tube section 24 and flexible tube section 28 can not comprise flexible tube section, but can comprise pipeline section or be configured to comprise and draw the conduit of other type of airflow guiding.Therefore, in certain embodiments, flexible tube section 24 and flexible tube section 28 can be made up of the material making flexible tube section 24 and flexible tube section 28 be essentially the such as rubber of flexibility, and in other embodiments, flexible tube section 24 and flexible tube section 28 can be made up of the metal making flexible tube section 24 and flexible tube section 28 be essentially rigidity.In the illustrated embodiment in which, flexible tube section 24 at one end place of portion is connected to pipeline section 34, and is connected to silencer 26 at opposed end place.
Silencer 26 is configured to through type silencer.Therefore, silencer 26 does not comprise and usually appears at baffle plate in silencer or other obstacle.On the contrary, silencer 26 has the inside of general hollow, and described inside can be customized to certain size, profile, and is made up of the material being configured to be crossed by reduction air circulation the non-hope noise volume that electronically actuated valve 30 produces.One of ordinary skilled in the art has known the technology of this kind of reduction noise, design and configuration.As mentioned above, one end of silencer 26 is connected to flexible tube section 24.The opposite end of silencer 26 is connected to flexible tube section 28.
Electronically actuated valve 30 can comprise the valve of any type that effectively can control (that is, optionally allow and forbid) air stream.Such as, in certain embodiments, electronically actuated valve 30 can comprise poppet valve or disk valve.Electronically actuated valve 30 comprises electronic building brick (such as screw actuator), and described electronic building brick is well-known in this area and it allows electronically actuated valve 30 to activate with electronics and/or long-range mode.By configuring by this way, can by passenger or other user optionally long-range stopping and the air stream that starting by ventilation system 12.In other embodiments, when not departing from the present invention's instruction, ventilation system 12 can not use electronically actuated valve, but can use mechanically actuated valve.
In the illustrated embodiment in which, electronically actuated valve 30 is fixed to bottom panel 20 by multiple threaded fasteners 31.The downstream part of electronically actuated valve 30 is connected to flexible tube section 28, and the upstream portion of electronically actuated valve 30 is connected to the flexible pipe 32 being configured to supply forced air.Therefore, when electronically actuated valve 30 is opened, the air (low pressure) on electronically actuated valve 30 downstream and the pressure reduction between the air (high pressure) on electronically actuated valve 30 upstream side cause air by electronically actuated valve 30 flow further downstream.
As shown in Figure 2, the forced air supplied by flexible pipe 32 will be advanced through electronically actuated valve 30 before entering into cabin, cabin 10, by flexible tube section 28, by silencer 26, by flexible tube section 24, by nozzle mount pad 22, and by nozzle 16.Electronically actuated valve 30 is spaced apart by flexible tube section 24, silencer 26 and flexible tube section 28 and nozzle 16.By being arranged in such a way, any undesirable noise that the air stream supplied by flexible pipe 32 produces through the intraware of electronically actuated valve 30 at it dissipated having enough chances before entering cabin, cabin 10.In addition, as discussed above, silencer 26 is designed and is configured to suppress undesirable noise to be delivered in cabin, cabin 10 by ventilation system 12 further.Therefore, when the air stream by ventilation system 12 is discharged at the air stream that nozzle 16 sentences high relative velocity, compared with the air stream of being discharged by traditional ventilation system, this discharge will be relatively quiet.In other embodiments, ventilation system 12 can not comprise silencer 26.In such systems, itself significantly the volume of not wishing noise sent from nozzle 16 can be reduced by spaced apart to nozzle 16 and electronically actuated valve 30 (if or using mechanical valve, then with mechanical valve).In such systems, the distance measurements between nozzle 16 and electronically actuated valve 30 can be enough to make system quiet, or at least reduces the noise caused by Dynamic System.
Fig. 3 is the schematic diagram that ventilation system 12 is shown.Continue, with reference to Fig. 1-2, in figure 3, to illustrate in greater detail electronically actuated valve 30 and nozzle 16.In the illustrated embodiment in which, illustrate that electronically actuated valve 30 is poppet valve.The button switch 36 being configured to actuating electronic activated valve 30 is connected to electronically actuated valve 30.Button switch 36 extends in the below of electronically actuated valve 30, and can be touched by the passenger be seated in cabin, cabin 10.Button switch 36 is electrically connected to the mechanism's (such as, screw actuator) be integrated in electronically actuated valve 30, and it will open, and close and/or partly open electronically actuated valve 30 so when energized.Should be understood that, although illustrated that button switch 36 is the switch of type of button, also can use the switch of other type any effectively optionally connecting electronically actuated valve 30 when not departing from the present invention's instruction.
Fig. 3 also illustrates in greater detail nozzle 16.As shown in the figure, nozzle 16 has roughly spherical structure, and it allows nozzle 16 to rotate around X-axis and Y-axis two axles relative to nozzle mount pad 22.This provides larger degree of freedom and alerting ability to the passenger in cabin, cabin 10 selecting to be discharged by nozzle 16 in the direction of air stream.The intraware of nozzle 16 is also shown.Such as, nozzle 16 comprises path 38, and it is configured to guide and accelerate air circulation and crosses ventilation system 12 to form the air stream of the high relative velocity of being discharged by nozzle 16.Nozzle 16 is also equipped with fibula 40, and it is positioned at the upstream portion office in path 38.Fibula 40 is axisymmetric substantially, and profile is for having common aerofoil profile.By multiple tab member 42, fibula 40 is remained on position suitable in path 38.Path 38, fibula 40 and tab member 42 will be discussed in more detail below.
Fig. 4 is the more detailed cutaway view that nozzle 16 is shown.Nozzle 16 comprises the entrance 44 being positioned at nozzle 16 upstream end thereof place.Nozzle 16 also comprises the outlet 46 being positioned at nozzle 16 downstream end place.Path 38 extends to outlet 46 from entrance 44, and has the cross-sectional plane of the circular along its axial length.Therefore, entrance 44 is circular substantially and has diameter D1, and outlet 46 is substantially circle and has diameter D2.As shown in the figure, D1 is greater than D2.Therefore, when air circulation cross path 38 enter to downstream skidding time, its will run into will hinder its flowing the path that narrows.Mass flowrate, relation between speed and cross-sectional area are well-known, and are represented by following equation:
R＝A*V
In above-mentioned equation, variable R represents mass flowrate, and variables A represents that its conduit cross section area is crossed in air circulation, and variable V represents the speed of air stream.In ventilation system 12, mass flowrate keeps constant substantially, and its reason is that corresponding difference between the cross-sectional area of difference between D1 and D2 and entrance 44 and the cross-sectional area of outlet 46 is seriously to being enough to significantly affect mass flowrate.Therefore, when nozzle 16 is crossed in air circulation, when air stream runs into the cross-sectional area narrowed in path 38, it will speed up higher speed to keep constant mass flowrate.One denier air stream reaches outlet 46, then, when flowing to entrance 44 with air compared with its speed had, air stream moves with remarkable higher speed.As can be seen from equation above, the speed leaving the air stream of nozzle 16 depends on the cross-sectional area of outlet 46, and can calculate in a relatively accurate manner.This speed will be called as exit velocity in this article.
Can cause sending the volume of not wishing noise by ventilation system by the acceleration of the air stream of the nozzle of conventional ventilating system.Moved toward side, upstream by the position of generating portion being accelerated, fibula 40 contributes to eliminating this problem.Accelerate by moving part toward side, upstream, the undesirable noise produced by this acceleration moves away from the passenger be seated in cabin, cabin 10 further, thus can hear less undesirable noise.In addition, the upstream side position of fibula 40 provides longer distance to the stream leaving nozzle and becomes fully expansion and stable stream.Guarantee that stable flowing also contributes to reducing undesirable noise at nozzle exit.Fibula 40 realizes above-mentioned effect by serving as encumbrance to air stream when entering entrance 44.The obstruction that caused by fibula 40 reduce air stream by cross-sectional area.Reduction on cross-sectional area as above accelerates to higher speed by causing air, to keep constant mass flowrate.Therefore, compared with there is not the speed of fibula 40 Airflow movement, the air stream entering entrance 44 moves with much higher speed.
When air stream continues to be advanced through nozzle 16, pass through between the surface 48 and the surface 50 in path 38 of fibula 40, and the obstruction of the reduction cross-sectional area in path 38 will be subject to further.The cross-sectional area of the reduction in path 38 will accelerate air stream further and to go directly exit velocity.Because the ramp-up rate (result as fibula 40) when air flows to entrance 44 and because the corresponding minimizing in acceleration amount that must be provided by path 38 in order to air stream is accelerated through exit velocity, by nozzle 16 send do not wish that the volume of noise and nozzle 16 do not comprise fibula 40 when compared with lower.
The additional benefit of the reduction noise provided by fibula 40 is provided.Such as, fibula 40 is arranged so that the air stream being advanced through nozzle straightens.This can prevent the eddy current that can produce when air stream enters in entrance 44 from path 22 transfer.This is very useful when nozzle 16 rotates and makes the air stream direction entered in entrance 44 not aim at path 38.The other benefit provided by fibula 40 be its produce evenly velocity distribution.Will close to zero velocity in the flowing velocity of boundary, and speed intracardiac in stream will be the highest.Flow velocity when fibula is made air stream to launch to enter in path 38 and left by outlet 46 becomes more even.The final spectral content of noise is to lower frequency deviation.This skew will reduce peak noise level and will change the noise spectrum be fused in the similar spectral content of aircraft cabin noise spectrum.This reduction of peak noise level and the fusion of spectral content will reduce the property heard of noise, and its reason is that it becomes and is difficult to distinguish with the existing noise in aircraft cabin.
In the illustrated embodiment in which, fibula 40 has tapered profiles, and like this when air passes through between surface 48 and surface 50, the distance L1 between surface 48 and surface 50 keeps constant substantially.By the distance between surface 48 and surface 50 is kept constant, fibula 40 can not give extra acceleration for the air stream passed through between these two surfaces.Find that this configuration causes the minimum decibel readings at outlet 46 place.In other embodiments, it is desirable to changing the distance between surface 50 and surface 48 along the axially different position in path 38, and these modification can be implemented when not departing from disclosure instruction.
Fig. 5 is the axial view of nozzle 16 upstream portion.In this view, the cross-sectional area of the circular in path 38 is clearly visible.Continue with reference to Fig. 1-4, the air stream entered in entrance 44 runs into the obstacle of fibula 40 form.Therefore when air drifts dynamic by being only limitted to during nozzle 16 advance between the surface 48 of fibula 40 and surface 50.As mentioned above, cause the reduction on entrance 44 cross-sectional area at the fibula 40 of entrance 44 existence, this causes the acceleration of air stream.
As shown in Figure 5, fibula 40 is attached to nozzle 16, and is positioned in path 38 by tab member 42.In an illustrated embodiment, use three tab member 42 that fibula 40 is attached to nozzle 16.In other embodiments, more or less tab member 42 can also be used.Tab member 42 extends radially through path 38, and therefore it will run into and partly hinders the air stream along path 38 movement.As illustrated in the best in Fig. 6, tab member 42 is configured to have aerofoil profile to reduce the impact caused the air stream along path 38 movement.
Fig. 6 is the transparent view that tab member 42 is shown.Continue with reference to Fig. 1-5, tab member 42 is configured to the cross-sectional configuration with aerofoil profile.When air drift dynamic by path 38 time, this structure causes relatively minimum interference by air stream.Tab member 42 comprises the pair of engaging component 52 being convenient to tab member 42 is installed to nozzle 16.In other embodiments, additional coupling members can be provided tab member 42 is fixed to nozzle 16.
Fig. 7 is the diagram of circuit of the embodiment of the assemble method 54 illustrated according to the ventilation system of instruction of the present disclosure.Continue with reference to Fig. 1-6, in step 56, collect valve, conduit, nozzle and silencer.This valve can be mechanical valve or electronically actuated valve.Conduit can be pipe, pipeline, flexible pipe or analogue.In certain embodiments, nozzle can comprise calibrating nozzle, such as use in conventional ventilating system those, and in other embodiments, the fibula about nozzle 16 that above nozzle can be configured to be included in, institute discusses and describes.Silencer can comprise any traditional through type silencer, and inside that is that it has a general hollow or sound-absorbing is to catch noise when not hindering air to flow.In certain embodiments, ventilation system can not comprise silencer.In these embodiments, step 56 will not comprise and collect silencer to assemble.
In step 58, nozzle is installed near birdman cabin, like this nozzle placement is become to ventilate to passenger compartments.In certain embodiments, nozzle can be arranged in the overhead bin that is arranged at above passenger seat.In other embodiments, nozzle can be arranged on after the cabin near any structure, panel, fixture and/or passenger cabin.Such as, in certain embodiments, the rear of the below or wallboard that ventilation system are arranged on floor panel can be favourable or preferred.
In step 60, valve is positioned at the position of opening with nozzle pitch near passenger cabin.In certain embodiments, valve can be positioned on the same panel that nozzle is installed to below and/or be installed in same panel that nozzle is installed to.In other embodiments, valve can be installed to/be positioned at after other panel any and/or cabin, and can locate away from nozzle.
In step 62, by tubes connection between the output and the entrance of nozzle of valve, make valve and nozzle via conduit and fluidly couple each other.Therefore, form the valve of ventilation system, nozzle becomes with conduits configurations provides ventilation to birdman cabin.In certain embodiments, conduit can be configured to bayonet fitting or otherwise joins described nozzle and valve to.In other embodiments, conduit can be assembled to described nozzle and valve, then uses any suitable adaptor union that conduit is attached to nozzle and valve.By configuring in the said manner, one end of conduit is positioned to receive the air stream from valve, and the other end of conduit is positioned to airflow to deliver to nozzle.By assembling ventilation system by this way, valve and nozzle are spaced apart from each other, but still fluidly couple each other.Permission fluid such as air stream is sent to nozzle from valve by this, provides the distance between two assemblies (that is, valve and nozzle) simultaneously.This distance was dissipated allowing to cross by air circulation undesirable noise that valve causes before being discharged by nozzle.
In step 64, use wherein in the embodiment of silencer, silencer is connected to conduit, and described silencer is arranged between valve and nozzle, and silencer and nozzle and valve are fluidly coupled.By being arranged in such a way, silencer be positioned to receive from valve air stream and airflow is delivered to nozzle.There is silencer in ventilation system and the suppression strengthening ventilation system is further crossed by air circulation the ability of not wishing the volume of noise that valve causes.
Although propose at least one exemplary embodiment in the detailed description above, it should be understood that to there is a large amount of modification.It is to be further understood that an exemplary embodiment or multiple exemplary embodiment are only examples, and be not intended to limit the scope of the invention by any way, applicability or configuration.On the contrary, detailed description above facilitates guide (road map) by what be provided for an enforcement exemplary embodiment to those skilled in the art.Should be understood that, when not departing from the disclosure scope as proposed in the appended claims, various change can be carried out to element function described in the exemplary embodiment and layout aspect.
Claims (20)
1. the ventilation system for ventilating to the passenger cabin of aircraft, described ventilation system comprises:
Nozzle, it is suitable for installing near described interior of aircraft, and it is configured to air stream to be directed to described passenger compartments;
Valve, itself and described nozzle pitch are opened and are positioned at the upstream side of described nozzle, and described valve is configured to the air stream controlling to described nozzle; And
Conduit, described valve is fluidly couple to described nozzle by it, and described conduits configurations becomes described air stream is sent to described nozzle from described valve.
2. ventilation system according to claim 1, wherein said nozzle arrangement becomes to accelerate described air stream when described air stream flows through described nozzle, thus forms described air stream.
3. ventilation system according to claim 2, wherein said nozzle comprises transition zone, described transition zone has the first cross-sectional area in described transition zone upstream portion office and the second cross-sectional area in described transition zone downstream portion office, and wherein said first cross-sectional area is greater than described second cross-sectional area.
4. ventilation system according to claim 3, wherein said first cross-sectional area and described second cross-sectional area all have circular structure.
5. ventilation system according to claim 3, wherein said nozzle comprises the fibula be arranged in described transition zone.
6. ventilation system according to claim 5, wherein said transition zone has first surface, and wherein said fibula has second surface, the equal distance and a part for wherein said first surface and the appropriate section of described second surface are separated by.
7. ventilation system according to claim 5, wherein said fibula is attached to described nozzle by multiple fin.
8. ventilation system according to claim 7, each fin of wherein said multiple fin extends through the path formed by the second surface of the first surface of described transition zone and described fibula, and wherein each fin is configured to aerofoil profile at least in part.
9. ventilation system according to claim 1, wherein said nozzle is adjustable.
10. ventilation system according to claim 9, wherein said nozzle has roughly spherical periphery.
11. ventilation systems according to claim 1, wherein said valve is electronically actuated valve.
12. ventilation systems according to claim 1, wherein said conduit comprises flexible pipe.
13. 1 kinds of ventilation systems for ventilating to the passenger cabin of aircraft, described ventilation system comprises:
Nozzle, it is suitable for installing near interior of aircraft, and it is configured to air stream to be directed to described passenger compartments;
Valve, itself and described nozzle pitch are opened and are positioned at the upstream side of described nozzle, and described valve is configured to the air stream controlling to described nozzle;
Conduit, described valve is fluidly couple to described nozzle by it, and described conduits configurations becomes described air stream is sent to described nozzle from described valve; And
Silencer, it fluidly couples with described conduit, thus silencer is crossed in described air circulation, and silencer is configured to when described air stream flows through described silencer from described absorbed acoustic energy.
14. ventilation systems according to claim 13, wherein said silencer is through type silencer.
15. according to ventilation system described in claim 13, and wherein said silencer is arranged between the first paragraph of described conduit and the second segment of described conduit.
16. ventilation systems according to claim 13, wherein said nozzle comprises transition zone, described transition zone has the first cross-sectional area in described transition zone upstream portion office and the second cross-sectional area in described transition zone downstream portion office, and wherein said first cross-sectional area is greater than described second cross-sectional area.
17. ventilation systems according to claim 16, wherein said nozzle comprises the fibula be arranged in described transition zone.
18. ventilation systems according to claim 17, wherein said transition zone has first surface, and described fibula has second surface, the equal distance and a part for wherein said first surface and the appropriate section of described second surface are separated by.
19. 1 kinds, for the assemble method of ventilation system ventilated to the passenger cabin of aircraft, said method comprising the steps of:
Collect nozzle, valve and conduit;
Near the described passenger cabin described nozzle being arranged on described aircraft, described like this nozzle placement becomes to ventilate to described passenger compartments;
Described valve is positioned at the position of opening with described nozzle pitch near described passenger cabin; And
By described tubes connection between the output and the entrance of described nozzle of described valve, make described valve and described nozzle via described conduit and fluidly couple each other, and being configured to provide ventilation to the described passenger cabin of described aircraft.
20. methods according to claim 19, comprise the steps: further collect silencer and described silencer is connected to described conduit, described silencer is arranged between described valve and described nozzle, and described silencer is fluidly coupled with described nozzle and described valve.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/288,796 | 2011-11-03 | ||
| US13/288,796 US9550574B2 (en) | 2011-11-03 | 2011-11-03 | Ventilation system and method of assembly |
| PCT/US2012/063222 WO2013109332A1 (en) | 2011-11-03 | 2012-11-02 | Ventilation system and method of assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104321253A true CN104321253A (en) | 2015-01-28 |
Family
ID=48224003
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280054124.7A Pending CN104321253A (en) | 2011-11-03 | 2012-11-02 | Ventilation system and method of assembly |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US9550574B2 (en) |
| EP (1) | EP2773559A4 (en) |
| CN (1) | CN104321253A (en) |
| CA (1) | CA2862004A1 (en) |
| WO (1) | WO2013109332A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113573923A (en) * | 2019-04-03 | 2021-10-29 | 宝马股份公司 | Device for ventilating the passenger compartment of a motor vehicle |
| CN113573923B (en) * | 2019-04-03 | 2024-04-23 | 宝马股份公司 | Device for ventilating a passenger compartment of a motor vehicle |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9815557B2 (en) * | 2012-09-20 | 2017-11-14 | Humbay Health, LLC | Aircraft humidifier |
| US10137992B2 (en) * | 2014-01-28 | 2018-11-27 | The Boeing Company | Remote controlled air nozzles and methods of assembling the same |
| WO2016027183A1 (en) * | 2014-08-21 | 2016-02-25 | Bombardier Inc. | Retractable air gasper apparatus |
| US11059592B2 (en) * | 2016-10-13 | 2021-07-13 | Gulfstream Aerospace Corporation | Coaxial fluid vent and electronic control for a fluid valve for aircraft |
| WO2019198572A1 (en) * | 2018-04-11 | 2019-10-17 | 株式会社デンソー | Air discharge device |
| FR3086585B1 (en) * | 2018-09-27 | 2020-09-04 | Valeo Systemes Thermiques | AUTOMOTIVE VEHICLE VENTILATOR, DEVICE AND METHOD FOR THERMAL MANAGEMENT USING SUCH A MOTOR VEHICLE VENTILATOR |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2516805A (en) * | 1946-11-01 | 1950-07-25 | Cons Vultee Aircraft Corp | Ventilating apparatus |
| US2854913A (en) * | 1956-12-13 | 1958-10-07 | United Aircraft Corp | Flow control means for an aircraft air conditioning system |
| US3436522A (en) * | 1964-12-15 | 1969-04-01 | Union Carbide Corp | Gas shielded arc welding torch |
| US6619589B2 (en) * | 2002-01-28 | 2003-09-16 | The Boeing Company | Flight crew and attendant rest environmental control system |
| US20100093267A1 (en) * | 2008-10-10 | 2010-04-15 | Airbus Operations Gmbh | Service apparatus for a transportation means |
| US20100240290A1 (en) * | 2007-10-18 | 2010-09-23 | Airbus Operations Gmbh | System And Method For Air Conditioning At Least One Partial Region Of An Airplane |
| US20110240796A1 (en) * | 2008-11-20 | 2011-10-06 | Airbus Operations Gmbh | Supply unit for flexible supply channels |
Family Cites Families (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| USRE23445E (en) * | 1951-12-18 | Aircraft cabin pressure regulating | ||
| GB533791A (en) * | 1939-08-19 | 1941-02-20 | Carrier Engineering Co Ltd | Improvements in or relating to ventilating devices |
| US2441088A (en) * | 1944-02-26 | 1948-05-04 | Bendix Aviat Corp | Aircraft cabin pressure regulating means |
| US2596909A (en) * | 1948-01-15 | 1952-05-13 | Wemac Company | Valve device |
| GB718143A (en) * | 1952-04-25 | 1954-11-10 | Winsor Engineering Company Ltd | Improvements relating to heating and ventilating apparatus |
| NL262265A (en) * | 1960-03-11 | 1900-01-01 | ||
| GB1161111A (en) * | 1965-05-25 | 1969-08-13 | Humber Ltd | Ventilating valves for vehicles |
| JPS501798Y2 (en) * | 1972-04-12 | 1975-01-18 | ||
| GB1394462A (en) * | 1972-05-11 | 1975-05-14 | Creators Ltd | Swivel nozzle for heating or ventilating system |
| DE2404062C3 (en) * | 1974-01-29 | 1978-04-20 | Draegerwerk Ag, 2400 Luebeck | Breathing gas supply regulators, in particular for high-altitude breathing apparatus |
| US4396157A (en) * | 1981-03-17 | 1983-08-02 | Elstat Limited | Nozzle for spraying apparatus |
| US5099752A (en) * | 1989-12-11 | 1992-03-31 | Dynamic Educational Systems, Inc. | Enclosure ventilation and temperature apparatus |
| US5338254A (en) * | 1992-12-22 | 1994-08-16 | Midwest Research Institute | Increasing jet entrainment, mixing and spreading |
| US5399119A (en) * | 1993-08-10 | 1995-03-21 | Puritan-Bennett Corporation | Air valve device having flush closing nozzle |
| DE19509773C1 (en) * | 1995-03-17 | 1996-06-27 | Daimler Benz Aerospace Airbus | Ventilating system for reducing concentration of impurities in aircraft passenger area |
| US6610116B1 (en) * | 2000-08-07 | 2003-08-26 | Neal H. Avery | Air filter system |
| US7014557B2 (en) * | 2003-07-23 | 2006-03-21 | Goodrich Hella Aerospace Lighting Systems Gmbh | Outlet device for the interior of a vehicle |
| FR2876172B1 (en) * | 2004-10-01 | 2008-07-11 | Peugeot Citroen Automobiles Sa | DEVICE FOR THE ACOUSTICAL ATTENUATION OF A VENTILATION PIPE OF A MOTOR VEHICLE AND METHOD OF MAKING SUCH A DEVICE |
| US7546899B2 (en) * | 2005-10-05 | 2009-06-16 | Arrowhead Products Corporation | Lightweight polymer muffler apparatus and method of making same |
| US8795041B2 (en) * | 2006-11-28 | 2014-08-05 | Shimadzu Corporation | Conditioned air supply method and supply system for aircraft |
| US8016211B2 (en) * | 2007-03-30 | 2011-09-13 | Aerojet-General Corporation | Pintle-controlled propulsion system with external ring actuator |
| DE102009025873A1 (en) * | 2009-05-27 | 2010-12-02 | Saar-Metallwerke Gmbh | Use of a height compensating nozzle |
| DE102009029875A1 (en) * | 2009-06-22 | 2010-12-30 | Airbus Operations Gmbh | Flow restrictor and use of a flow restrictor in an air distribution system of an air conditioning system of an aircraft |
| DE102009058227A1 (en) * | 2009-12-14 | 2011-06-16 | Airbus Operations Gmbh | Acoustically optimized air conditioning components |
| US8601826B2 (en) * | 2011-01-20 | 2013-12-10 | Hamilton Sundstrand Corporation | Recirculation heat exchanger outlet header |
-
2011
- 2011-11-03 US US13/288,796 patent/US9550574B2/en active Active
-
2012
- 2012-11-02 EP EP12865653.5A patent/EP2773559A4/en not_active Withdrawn
- 2012-11-02 CA CA2862004A patent/CA2862004A1/en not_active Abandoned
- 2012-11-02 CN CN201280054124.7A patent/CN104321253A/en active Pending
- 2012-11-02 WO PCT/US2012/063222 patent/WO2013109332A1/en active Application Filing
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2516805A (en) * | 1946-11-01 | 1950-07-25 | Cons Vultee Aircraft Corp | Ventilating apparatus |
| US2854913A (en) * | 1956-12-13 | 1958-10-07 | United Aircraft Corp | Flow control means for an aircraft air conditioning system |
| US3436522A (en) * | 1964-12-15 | 1969-04-01 | Union Carbide Corp | Gas shielded arc welding torch |
| US6619589B2 (en) * | 2002-01-28 | 2003-09-16 | The Boeing Company | Flight crew and attendant rest environmental control system |
| US20100240290A1 (en) * | 2007-10-18 | 2010-09-23 | Airbus Operations Gmbh | System And Method For Air Conditioning At Least One Partial Region Of An Airplane |
| US20100093267A1 (en) * | 2008-10-10 | 2010-04-15 | Airbus Operations Gmbh | Service apparatus for a transportation means |
| US20110240796A1 (en) * | 2008-11-20 | 2011-10-06 | Airbus Operations Gmbh | Supply unit for flexible supply channels |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113573923A (en) * | 2019-04-03 | 2021-10-29 | 宝马股份公司 | Device for ventilating the passenger compartment of a motor vehicle |
| CN113573923B (en) * | 2019-04-03 | 2024-04-23 | 宝马股份公司 | Device for ventilating a passenger compartment of a motor vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2013109332A1 (en) | 2013-07-25 |
| US9550574B2 (en) | 2017-01-24 |
| EP2773559A1 (en) | 2014-09-10 |
| CA2862004A1 (en) | 2013-07-25 |
| US20130115868A1 (en) | 2013-05-09 |
| EP2773559A4 (en) | 2015-08-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104321253A (en) | Ventilation system and method of assembly | |
| KR102190027B1 (en) | Thermal system with high aspect ratio vents | |
| JP5460952B2 (en) | Air inlet apparatus used in connection with a high speed levitating movable platform and used on a jet aircraft fuselage, aircraft, and method for forming an inlet on an outer surface of a jet aircraft fuselage | |
| US9810147B2 (en) | Angled inlet system for a precooler | |
| EP2868581B1 (en) | Inlet system having dual inlets | |
| US9950592B2 (en) | Line register | |
| JP6516547B2 (en) | Duct structure and aircraft exhausted through a pressure control valve | |
| US20090270022A1 (en) | Climate control duct architecture for a vehicle | |
| US20100087131A1 (en) | Integrated air supply device | |
| US20170089471A1 (en) | Ventilation systems and gasper valves with flexible components | |
| EP2824033B1 (en) | Apparatus for acoustic resonance mitigation | |
| US11679870B2 (en) | Apparatus for reducing drag of a transverse duct exit flow | |
| US20100317277A1 (en) | Air outlet | |
| US9011216B1 (en) | Diversion directional nozzle | |
| US20130252530A1 (en) | Air distribution arrangement for use with vehicle hvac system and method of distributing air | |
| KR101702223B1 (en) | A railway vehicles for duct have the function even distribution | |
| US11059592B2 (en) | Coaxial fluid vent and electronic control for a fluid valve for aircraft | |
| RU2094307C1 (en) | Transport aircraft with blunted tail section of fuselage | |
| EP3523197B1 (en) | Noise reducing air duct | |
| JP2014201271A (en) | Ship air conditioner | |
| EP3536616B1 (en) | Dual tube silencer for separate gas flows |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150128 |